Discharge tube for magazine rocket launcher



Dec. 6, 1955 Filed NOV. 4, 1948 DISCHARGE L. O. BERGSTROM TUBE FORMAGAZINE ROCKET LAUNCHER 2 Sheets-Sheet l @RII NVENTQFL Lms @SQME @ERGETRM Dec. 6, 1955 1 o. BERGSTROM DISCHARGE TUBE FOR MAGAZINE ROCKETLAUNCHER Filed Nov. 4, 1948 2 Sheets-Sheet 2 Fl'h.

IIIIIW.vmllllrllllftllllvlmm DISCHARGE TUBE FOR MAGAZINE ROCKET LAUNCHERLars O. Bergstrom, Bofors, Sweden, assignor to Aktiebolaget Bofors,Bofors, Sweden Application November 4, 1948, Serial No. 58,247 Claimspriority, application Sweden November 7, 1947 2 Claims. (Cl. 89-1.7)

The present invention relates to a rapid re rocket launcher.

The launcher of the present invention is suitable for use withpointed-nosed self-propelled rockets individually encased in open endedsleeves. The rockets are self-propelled in rapid succession through acommon discharge tube. A magazine is provided for retaining the rocketsand an automatic feeding device advances the rockets simultaneously inlaterally spaced relationshiprtoward an ultimate or discharge positionwhichV is adjacent to and in alignment with the discharge tube.

The discharge rate of the rocket launcher of the present invention isconsiderably increased by the provision of an enlarged rearwardly haringportion in the discharge tube adjacent to the feeding device. Thisenlarged portion communicates with Vthe rocket which is in a penultimateposition immediately adjacent to the ultimate or-discharge position andthe flaring portion is shaped to receive and guide the nose of therocket which is ready to advance from the penultimate position to theultimate or discharge position and to direct this rocket into thedischarge tube during the combined self-propelled forward movement ofthe rocket and its lateral advance toward the discharge position by thefeeding device.

Thus, the aring portion of the discharge tube permits a rocket tocommence its forward self-propelled movement as it moves laterally intoalignment with the discharge tube and the interval between thedischarges of successive rocketsis materially reduced. p

With the present rocket launcher, it is not necessary to advance eachrocket successively to the dischargeposition, ignite the rocket, andthen wait in the usual manner for it to enter the discharge tubecompletely before the next rocket may commence its self-propelledforward movement. While one rocket is in transit in the discharge tube,the next rocket is already in a self-propelled condition and isgradually moving forwardly into the enlarged portion of the dischargetube.

Various objects, features and advantages of the invention will becomeapparent upon reading the following specication together with theaccompanying drawing forming a part hereof:

Referring to the drawing: p

Figure l is a diagrammatic side view of a preferred embodiment of theinvention, shown partly in section.

Figure 2 is a transverse sectional view taken along the line lI-II ofFig. l, looking rearwardly in the direction of the arrows. p

Figure 3 is a plan sectional view taken along the line IlI III ofFig. 1. V

Figure 4 is an enlarged transverse sectional view taken along the linelV-IV of Fig. 3, looking forwardly in the direction of the arrows.

Figure 5 is an enlarged fragmentary view of the lower portion of Fig. 2.

Figure 6 is a transverse sectional view taken along the line VI VI ofFig. 3, looking rearwardly in the direction of the arrows.

Vntecl States Patent() formed of cardboard or the like and each sleeve 2acts as a guide for its encased rocket 1 when the encased rocket firststarts moving forwardly in the direction of re. The series of rockets 1is laterally pressed toward the ultimate position of discharge at whicheach rocket 1 vacates its tubular sleeve 2. by means of a spring pressedlazy tongs 4. The lazy tongs 4 comprises a plurality of laterallyextending compression springs 5 and centrally disposed compressionsprings 6 which act to extend the lazy tongs 4 and cause the encasedrockets 1 to advance laterally and simultaneously toward the ultimateposition of discharge. lf the magazine is placed vertically, the feedingmay also be effected merely through gravity. At one end piece of themagazine there is fixed a discharge tube 7, the part of which locatednearest to the magazine is tapered or flared, converging away from themagazine in the direction of fire so that this part when viewed insection along a plane paralleling the plane of the magazine formsapproximately an oblique cone. The bottommost sleeve is retained in theposition of discharge or ultimate position in alignment with thedischarge tube 7 by two stops 8 provided with supporting rollers 9. Eachstop 8 is controlled by a slotted arm 10, w 'ch is rigidly connectedwith a shaft 11 journalled in the bearing pieces 12 and 13, which are inturn mounted on the magazine 3. At the front end of the shaft 11 thereis ixed a short arm l5 which is actuated by a nose 16 mounted on arelease flap 17 pivotally mounted in one side of the discharge tube 7.To the rear end of the shaft 11 there is secured an arm 13, Fig. 4,provided with a notch 19 which engages a hook-shaped stop pawl 26. Thearm i8 and shaft 11 to which it is keyed are yieldingly urged in aclockwise direction as viewed in Fig. 4 by a helical tension spring 21.A button-ended control rod 22 is connected to the pawl Ztl. Thedischarge tube 7 is encased by a protective tube 24 provided with anumber of holes (not shown) for admitting cooling air.

27 designates U-shaped support beams for the magazine, 28 is a followerbar connected with the lazy tongs 4 and pushing the rockets towards theposition of discharge, 29 is a wall portion, 30 is a flange,V 31 anotherliange, 32 is a bolt to which the tension spring 21 is secured and 33 isrelease means for the springs 6.

The device functions as follows: v

When in initial position, the discharge sleeves'of the rockets are heldbarred against lateral advance by the two stops 3 which are controlledby the shaft 11 through slotted arms 10. Shaft l1 is locked by the stophook 20.

`The discharge of the rockets is normally started in such a manner thatthe rocket lying in the laterally most advanced discharge sleeve isignited by switching on the conventional electric ignitor 5G. The rocketthen moves longitudinally along the axial direction of the sleeve andpresses out the pivotally mounted ap 17. At the end of this movement,the nose 1e of the ilap 17 actuates the stop arm 15 so that the shaft 11is given a slight turn in the clockwise direction as viewed in Fig. 4.As a result, the pawl 20 is `released from the notch 19 in the arm It.VThe pawl 2), now free, is brought out of its locking position by acompression spring (not shown) which acts on the control rod 22. Unlessrestored manually as described below, the pawl 20 remains out of itslocking position where it can engage in notch 19 throughout the entireperiod of automatic operation of the device. During this period ofautomatic operation each rocket l in entering the discharge tube 7presses the flap 17 outwardly and holds it in this position until it haspassed the flap 17. While the ilap 17 is pressed outwardly it arrests'lateral advance of the rockets by holding the shaft 11 rotated in V'aeounterclockwise position Vas viewed in Figs. 4 and 6 or rotated in aclockwise position as viewed in Figs. 2 and 5. The shaft 11, while inthis rotated position, maintains the stop members 8 in blocking positionas illustrated in -Figs. 2 and 5 against the yielding action of tensionspring 21 (Pig. 4). After the rocket inthe discharge tube '7 has passedythe ilapf17, the spring 2l rotates the shaft 11 in the opposite`direction to withdraw the stop members S rom'their blocking positionsand permit the empty sleeve 25 (Fig. 5) at the ultimate dischargekposition to be ejected from the magazine as indicated in dotted outline(Fig. this ysleeve having just been completely vacated by the rear endportion of the discharged rocket which it previously encased before theap 17 was released. At the same time -that the empty sleeve is beingejected from the magazine, the sleeve 26 in-the penultimate positionadvances laterally. Before the sleeve '26 in penultimate positionreaches the ultimate position of discharge, however, its rocket isignited by the ignitor Sil and the nose of-the'rocket enters the daringportion of the discharge tube 7. While the sleeve 26 advances laterally,the ignited rocket which it contains simultaneously advances laterallyand moves forwardly along the direction of fire into the flaring portionof discharge tube '7 and in the course of this forward movement its noseis guided into the discharge tube 7 and thereafter it presses iiapleoutwardl-y so that the stop Vmembers 3 again move into blockingposition before the forwardly moving rocket has vacated its sleeve atthe ultimate discharge position.

The follower bar 28 of the lazy tongs 4 continuously presses on thesleeves Z so that the rockets are successively laterally advanced anddischarged until the magazine 3 is empty. Because the rocket whichis-advancing laterally from the penultimate position to the ultimateposition is already ignited and moving forwardly in the direction offire, the rockets may follow each other through the discharge tube 7 atextremely short intervals withoutwaiting for the next rocket which is tobe discharged to reach and come to rest -in the ultimate position beforeit is ignited.

Ignition of the rockets may be .performed in any convenient manner, forexample as shown in U. S. Patent No. 2,459,314. of conventionalconstruction is shown positioned adjacent Lto the rear of the magazine 3where it is arranged to ignite each rocket lI1 after it reaches theVpenultimate position and prior to the time when it arrives 4at theultimate position in alignment with the discharge tube '7. An energizingcircuit for the ignitor 50 is shown comprising a source of electricalenergy indicated as a battery landa control switch S2.

lf it is desired to stop the discharge of the rockets 1 before themagazine 3 is empty, the switch -52 is opened and upward pressure isexerted manually on the lower button-shaped end of control rod 22 (Fig.4). Control rod 22. then moves the pawl 26 into engagement in notch 19thus locking shaft 11 in the position where the stop members 3 are inthe blocking position which they assume each time that flap 17 ispressed outwardly.

The device according to the invention involves among other the followingadvantages: The cardboard sleeve 25 or 26 kencasing each rocket, whichsleeve can be said vto For purposes of illustration, an ignitor form therst part of the discharging tube, binds the 65 foldable steering wingsof the rocket and simplifies the electric current supply. The sleeve incombination with -the -tapernof-.therigid discharging `tube makes. anearlier discharge possible so that the tire rapidity is increased, sinceno inserting and fixing in a xed position is needed, as is the case inother automatic weapons. The sleeves are ejected only when the releaseap 17, placed in the rigid discharging tube is not actuated by thelatest rocket discharged fmmthemagaZine. At the start, the rockets areaccelerated by the lsprings 6 which operate in the moving direction, sothat the feeding obtains a great speed already from .the start. Evenfailing rockets are ejected, so that the discharging of the followingrockets goes on automatically. When a rocketis not tired, it falls.down, as the stops .8 will not come to the non-locking position.

Having now described my invention, what I claim as new and desire tosecure by Letters Patent is:

1. ln combination with a magazine for pointed-nosedself-propelledrockets, a common discharge tube through which saidrockets are to be successively self-propelled, feeding means lforsimultaneously and successively advancing a'pluraility of said rocketsin laterally spaced rela` tionship toward'an ultimate discharge positionadjacent tothe rear -end of said ydischarge tube and in alignmenttherewith satwhich ultimate position the most advanced of said lrocketin said feeding means may completely enter 4and pass through said tube,and means connected to said feeding means and actuated by each rocket inthe course of its passage through said discharge tube for advancing'saidfeeding means to br-ing the next rocket in saidV feeding means into saidultimate position, the provision of: a-rearwardly haring enlargedportion in said discharge tube `adjacent'to said feeding means, saidflaring Aportion'cotnnnlnicating with the rocket which is ina'penultimate position adjacent to said ultimate position, -saidfflaringyportion being shaped to receive the nose of-'saidlrocket :in saidpenultimate position and guide it into -said discharge tube during thecombined lateral advance V.of said ioeketby said feeding means from saidpenultimate positionto said lultimate position and forwardl movementwhich occurs when the said rocket is ignited as it leaves saidpenultimate position and prior to its arrival -at -said Vultimateposition.

2.1'The combination according to claim l, in which said rocketnctuatedmeans comprises a flap member pivotally mounted irrsaid .enlargedportion of said discharge tube, said flap member being actuated once byeach rocket in the course'of its longitudinal movement out of its sleeveandvthroughssaid discharge tube.

References `Cited in the ijle of `this patent f-U'NITED STATES PATENTS

